A high-bypass-ratio engine power transmission simulation device

Abstract

The application belongs to the technical field of aircraft structure strength test, and particularly relates to a large-bypass-ratio engine force transmission simulation device. The large-bypass-ratio engine force transmission simulation device is designed to be composed of 11 categories of a heading loading point, a gravity center two-side loading point, a main force transmission shaft simulation piece, a fan case front installation edge simulation piece, an intermediate case inner ring simulation piece, an intermediate case rear installation plane simulation piece, a turbine rear case simulation piece, an installation joint simulation piece, a lug simulation piece, a reverse thrust torque box front cover simulation piece and a reinforcing rib, by analyzing the connection of the large-bypass-ratio engine and the aircraft and according to the structural characteristics of the large-bypass-ratio engine. The engine mass, inertia, stiffness and installation interface are simulated, the loading points at various positions are provided, the simulation of the aero-engine load is realized by the combination of single-point simple loading, and the large-bypass-ratio aero-engine test loading problem in the aircraft strength test is solved.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing technology, and specifically relates to a force transmission simulation device for a high bypass ratio engine. Background Technology

[0002] Aircraft structural strength testing applies aerodynamic and inertial loads experienced by the aircraft during ground and flight to a real aircraft structure in the form of ground tests. This verifies the aircraft structure's ability to withstand these loads and is a reliable verification method to ensure aircraft safety. During structural strength testing, various loads transmitted by the engine need to be simulated at the aircraft's pylons. For high-bypass turbofan engines, their long overall length, large fan diameter, and significantly greater weight compared to other types of engines further increase the difficulty of structural strength testing. During structural strength testing, systems or devices unrelated to strength assessment, such as avionics and hydraulic conduits, can be omitted. However, those related to structural force transmission, such as actuators or landing gear, must be installed. To reduce the manufacturing cost of test components, simplify test loading, and facilitate test implementation, simple and easy-to-manufacture and assemble simulation devices can be used as accessories for the test components. The main function of the force transmission simulation device is to transmit loads equivalent to those of the real component and possess sufficient stiffness to ensure the accuracy of the strength test. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a high bypass ratio engine force transmission simulation device, comprising:

[0004] Front assembly, middle assembly and rear assembly;

[0005] The front assembly includes: a front section of the main transmission shaft, a fan housing front mounting edge simulation component and a center-of-gravity loading disk respectively mounted on the front end and middle of the front section of the main transmission shaft; the front mounting edge simulation component of the fan housing has a forward yaw loading disk with a single lug on the disk surface.

[0006] The mid-section assembly includes:

[0007] The main transmission shaft has a centrally welded disc. The disc is formed by radially connecting an inner ring of the intermediate housing, a rear mounting plane of the intermediate housing, and a front cover of the torque box. The disc also has a main mounting section simulation component installed on it.

[0008] The rear assembly includes: a rear section of the main transmission shaft, a loading disk on the rear side of the center of gravity mounted on the rear section of the main transmission shaft, a turbine rear casing simulator mounted at the end of the rear section of the main transmission shaft, an auxiliary mounting lug simulator and an auxiliary mounting section simulator mounted on the outer edge of the turbine rear casing simulator, and a rear yaw loading point on the end face of the turbine rear casing simulator.

[0009] The rear end of the front section of the main force transmission shaft is connected to the front end of the middle section of the main force transmission shaft, and the rear end of the middle section of the main force transmission shaft is connected to the front end of the rear section of the main force transmission shaft.

[0010] The engine force transmission simulation device is installed on the aircraft by bolting together the main mounting section simulation component and the auxiliary mounting section simulation component. The torque box front cover simulation component is connected to the aircraft fan cover by overlapping. The directional load is applied through the forward directional loading plate and the rear directional loading point, and the lateral and vertical loads are applied through the front loading plate and the rear loading plate of the center of gravity.

[0011] Preferably, the front section, middle section, and rear section of the main transmission shaft are circular tube structures with a certain wall thickness, used to simulate the external casing of the engine, support each functional section, and transmit the load between each functional section.

[0012] Preferably, the rear end of the front section of the main force transmission shaft, both ends of the middle section of the main force transmission shaft, and the front end of the rear section of the main force transmission shaft all have mounting edges for docking.

[0013] Preferably, I-shaped pads are provided between the front section and the middle section of the main force transmission shaft, and between the middle section and the rear section of the main force transmission shaft, to compensate for axial errors generated during the manufacturing and assembly of the axial engine force transmission simulation device.

[0014] Preferably, the front mounting edge of the fan casing has a first bolted reinforcing rib distributed circumferentially between the front mounting edge and the front section of the main transmission shaft, and the front loading plate of the center of gravity has a first welded reinforcing rib distributed circumferentially between the front loading plate and the front section of the main transmission shaft.

[0015] Preferably, the loading disk at the rear of the center of gravity is connected to the rear section of the main force transmission shaft by a plurality of circumferentially distributed second welded reinforcing ribs.

[0016] Preferably, the inner ring of the intermediate casing is connected to the middle section of the main transmission shaft by multiple circumferentially distributed second bolt-type reinforcing ribs.

[0017] Preferably, the rear section of the main force transmission shaft includes a first rear section of the main force transmission shaft and a second rear section of the main force transmission shaft, and the loading disk on the rear side of the center of gravity is installed between the first rear section of the main force transmission shaft and the second rear section of the main force transmission shaft.

[0018] This invention proposes a force transmission simulation device for a high bypass ratio engine with a simple shape and easy manufacturing and assembly to replace the existing engine test piece. It can transmit loads equivalent to those of the real part and has considerable stiffness, thereby ensuring the accuracy of the strength test.

[0019] By analyzing the connection between the high-bypass turbofan engine and the aircraft, and based on the structural characteristics of the high-bypass turbofan engine, the high-bypass turbofan engine force transmission simulation device was designed to consist of 11 major categories, including directional loading points, loading points on both sides of the center of gravity, main force transmission shaft simulation components, fan casing front mounting edge simulation components, intermediate casing inner ring simulation components, intermediate casing rear mounting plane simulation components, turbine rear casing simulation components, mounting section simulation components, lifting lug simulation components, thrust reverser torque box front cover simulation components, and reinforcing ribs. It simulates the engine's mass, inertia, stiffness, and mounting interface, and provides loading points at various locations. By combining simple single-point loading, it simulates the load on the aero-engine and solves the problem of loading in high-bypass turbofan engine tests during aircraft strength testing. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the engine power transmission simulation device.

[0021] Figure 2 This is a schematic diagram of the front-end assembly structure.

[0022] Figure 3 Schematic diagram of the front side of the middle section assembly structure.

[0023] Figure 4 Schematic diagram of the rear side of the middle section assembly structure.

[0024] Figure 5 Schematic diagram of the rear assembly structure. Detailed Implementation

[0025] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0026] like Figures 1-5 As shown, a high bypass ratio engine power transmission simulation device has a segmented design structure, as follows: Figure 1 As shown, it consists of a front assembly 1, a middle assembly 2, a rear assembly 3, a first I-shaped pad 4, and a second I-shaped pad 5.

[0027] Front section assembly 1: The front section assembly is composed of the forward yaw loading plate 6, the fan casing front mounting edge simulation part 7, the first bolt-connected reinforcing rib 8, the front section of the main transmission shaft 9, the first welded reinforcing rib 10, the center of gravity front loading plate 11, and the first main transmission shaft mounting edge 12, as follows. Figure 2As shown.

[0028] Mid-section assembly 2: The front-section assembly is composed of the second main transmission shaft mounting edge 13, the main transmission shaft mid-section 14, the second bolt-connected reinforcing rib 15, the intermediate housing inner ring simulation part 16, the intermediate housing rear mounting plane simulation part 17, the torque box front cover simulation part 18, the main mounting section simulation part 19, and the third main transmission shaft mounting edge 20, as follows. Figure 4 As shown.

[0029] Rear assembly 3: The rear assembly is composed of the fourth main transmission shaft mounting edge 21, the rear section of the first main transmission shaft 22, the second welded reinforcing rib 23, the rear loading plate 24, the rear section of the second main transmission shaft 25, the auxiliary mounting lug simulator 26, the auxiliary mounting section simulator 27, the turbine rear casing simulator 28, and the rear yaw loading point 29, as follows. Figure 5 As shown.

[0030] Assembly connection:

[0031] Front assembly 1: The forward yaw loading disk 6 is connected to the front mounting edge simulation component 7 of the fan casing by bolts. The front mounting edge simulation component 7 of the fan casing is connected to the front section 9 of the main transmission shaft by welding. The front section 9 of the main transmission shaft is connected to the front loading disk 11 of the center of gravity by welding. The front loading disk 11 of the center of gravity is connected to the first main transmission shaft mounting edge 12 by welding. The first bolt-connected reinforcing rib 8 is connected to the front mounting edge simulation component 7 of the fan casing and the front section 9 of the main transmission shaft by bolts. The first welded reinforcing rib 10 is connected to the front section 9 of the main transmission shaft and the front loading disk 11 of the center of gravity by welding.

[0032] Mid-section assembly Figure 4 The second main transmission shaft mounting edge 13 is connected to the middle section 14 of the main transmission shaft by welding. The middle section 14 of the main transmission shaft is connected to the inner ring simulation part 16 of the intermediate housing by welding. The inner ring simulation part 16 of the intermediate housing is connected to the rear mounting plane simulation part 17 of the intermediate housing by bolts. The rear mounting plane simulation part 17 of the intermediate housing is connected to the front cover simulation part 18 of the torque box by bolts. The inner ring simulation part 16 of the intermediate housing is connected to the third main transmission shaft mounting edge 20 by welding. The inner ring simulation part 16 of the intermediate housing is connected to the main mounting section simulation part 19 by bolts. The second bolt-connected reinforcing rib 15 is connected to the middle section 14 of the main transmission shaft and the inner ring simulation part 16 of the intermediate housing by bolts.

[0033] Rear assembly Figure 5The fourth main transmission shaft mounting edge 21 is connected to the rear section 22 of the first main transmission shaft by welding. The rear section 22 of the first main transmission shaft is connected to the loading plate 24 behind the center of gravity by welding. The loading plate 24 behind the center of gravity is connected to the rear section 25 of the second main transmission shaft by welding. The rear section 25 of the second main transmission shaft is connected to the turbine rear casing simulator 28 by welding. The turbine rear casing simulator 28 is connected to the rear yaw loading point 29 by bolts. The turbine rear casing simulator 28 is connected to the auxiliary mounting section lifting lug simulator 26 by bolts. The auxiliary mounting section lifting lug simulator 26 is connected to the auxiliary mounting section simulator 27 by bolts. The second welded reinforcing rib 23 is connected to the rear section 22 of the first main transmission shaft and the loading plate 24 behind the center of gravity by welding.

[0034] Engine power transmission simulation device Figure 1 The front assembly 1 is connected to the first I-shaped washer 4 and the middle assembly by bolts. Figure 2 The middle section assembly 2 is connected to the second I-shaped pad 5 and the rear section assembly by bolts. Figure 4 connect.

[0035] The engine force transmission simulation device is bolted to the aircraft via the main mounting section simulation component 19 and the auxiliary mounting section simulation component 27. The torque box front cover simulation component 18 is connected to the aircraft fan cowl via an overlapping connection. The test directional load can be applied through the forward directional loading plate 6 and the rear directional loading point 29, and through the forward center of gravity loading plate 11...

[0036] The rear loading disk 24 can apply lateral and vertical loads during testing. The number and location of loading points can be designed according to actual needs. To ensure the relative positions of the lateral and vertical loading points and the strength and stiffness of the loading points, the front loading disk 11 and the rear loading disk 24 adopt an integral circular distributed design. To ensure the smooth installation of the engine force transmission simulation device onto the aircraft, a first I-shaped pad 4 and a second I-shaped pad 5 are designed to compensate for axial errors caused by the manufacturing and assembly of the axial engine force transmission simulation device. The front section 9, the middle section 14, and the rear section 25 of the second main force transmission shaft simulate the external engine casing, responsible for supporting each functional section and realizing load transfer between each functional section. The dummy main force transmission shaft is designed as a circular tube structure with a certain wall thickness.

[0037] This application designs a novel engine force transmission simulation device, which overcomes the shortcomings of traditional real engine test parts, such as high production cost, long manufacturing cycle, and high modification risk.

[0038] 2. The engine force transmission simulation device adopts a segmented design, using a combination of bolted and welded reinforcing ribs to comprehensively improve the overall assemblability of the engine force transmission simulation device, while also reducing the impact of welding deformation.

[0039] 3. An I-shaped adjustment pad was designed to effectively compensate for assembly and manufacturing errors in the engine force transmission simulation device.

[0040] 4. The loading points on both sides of the center of gravity adopt an integral circular distributed design, which ensures the relative position of the lateral and vertical loading points, as well as the strength and stiffness of the loading points.

[0041] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A power transmission simulation device for a high bypass ratio engine, characterized in that, include: Front assembly (1), middle assembly (2) and rear assembly (3); The front assembly (1) includes: the front section of the main transmission shaft (9), the front mounting edge simulation component (7) of the fan housing and the front loading plate (11) of the center of gravity respectively installed at the front end and the middle of the front section of the main transmission shaft (9), and the front loading plate (6) of the fan housing front mounting edge simulation component (7) has a front yaw loading plate (6) with a single ear on the plate surface. The middle section assembly (2) includes: The main transmission shaft middle section (14) is welded to the disk, which is formed by radially connecting the intermediate casing inner ring simulation part (16), the intermediate casing rear mounting plane simulation part (17) and the torque box front cover simulation part (18); the disk is also equipped with the main mounting section simulation part (19); The rear assembly (3) includes: a rear section of the main transmission shaft, a loading disk (24) on the rear side of the center of gravity mounted on the rear section of the main transmission shaft, a turbine rear casing simulator (28) mounted at the end of the rear section of the main transmission shaft, an auxiliary mounting lug simulator (26) and an auxiliary mounting section simulator (27) mounted on the outer edge of the turbine rear casing simulator (28), and a rear yaw loading point (29) on the end face of the turbine rear casing simulator (28). The rear end of the front section (9) of the main force transmission shaft is connected to the front end of the middle section (14) of the main force transmission shaft, and the rear end of the middle section (14) of the main force transmission shaft is connected to the front end of the rear section of the main force transmission shaft. The engine power transmission simulation device is installed on the aircraft by bolting through the main mounting section simulation component (19) and the auxiliary mounting section simulation component (27). The torque box front cover simulation component (18) is connected to the aircraft fan cover by overlapping. The yaw load is applied through the forward yaw loading plate (6) and the rear yaw loading point (29). Lateral and vertical loads are applied through the front center of gravity loading plate (11) and the rear center of gravity loading plate (24).

2. The high bypass ratio engine force transmission simulation device as described in claim 1, characterized in that, The front section (9), middle section (14), and rear section of the main transmission shaft are circular tube structures with a certain wall thickness, used to simulate the external casing of the engine, support each functional section, and transmit the load between each functional section.

3. The high bypass ratio engine power transmission simulation device as described in claim 1, characterized in that, The rear end of the front section (9) of the main force transmission shaft, both ends of the middle section (14) of the main force transmission shaft, and the front end of the rear section of the main force transmission shaft all have main force transmission shaft mounting edges for docking.

4. The high bypass ratio engine force transmission simulation device as described in claim 3, characterized in that, I-shaped pads are provided between the front section (9) and the middle section (14) of the main force transmission shaft, and between the middle section (14) and the rear section of the main force transmission shaft, to compensate for axial errors caused by the manufacturing and assembly of the axial engine force transmission simulation device.

5. The high bypass ratio engine force transmission simulation device as described in claim 1, characterized in that, The front mounting side simulation component (7) of the fan casing has a first bolted reinforcing rib (8) distributed circumferentially between it and the front section (9) of the main force transmission shaft, and the front loading disk (11) of the center of gravity has a first welded reinforcing rib (10) distributed circumferentially between it and the front section (9) of the main force transmission shaft.

6. The high bypass ratio engine force transmission simulation device as described in claim 1, characterized in that, The loading disk (24) at the rear of the center of gravity is connected to the rear section of the main force transmission shaft by multiple second welded reinforcing ribs (23) distributed circumferentially.

7. The high bypass ratio engine power transmission simulation device as described in claim 1, characterized in that, The intermediate casing inner ring simulation component (16) is connected to the middle section (14) of the main force transmission shaft by multiple circumferentially distributed second bolt-type reinforcing ribs (15).

8. The high bypass ratio engine force transmission simulation device as described in claim 1, characterized in that, The rear section of the main transmission shaft includes a first main transmission shaft rear section (22) and a second main transmission shaft rear section (25), and a loading disk (24) on the rear side of the center of gravity is installed between the first main transmission shaft rear section (22) and the second main transmission shaft rear section (25).

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